Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

GOE 460 AIRFOIL (goe460-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: GOE 460 AIRFOIL (goe460-il)
Reynolds number: 500,000
Max Cl/Cd: 50.57 at α=9.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe460-il-500000-n5.txt
Download as CSV file: xf-goe460-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 460 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -19.750  -1.0716   0.09212   0.08702  -0.0526   1.0000   0.0465
 -19.500  -1.0783   0.08816   0.08300  -0.0539   1.0000   0.0471
 -19.250  -1.0838   0.08439   0.07915  -0.0551   1.0000   0.0478
 -19.000  -1.0876   0.08089   0.07557  -0.0561   1.0000   0.0487
 -18.750  -1.0905   0.07755   0.07215  -0.0570   1.0000   0.0493
 -18.500  -1.0944   0.07415   0.06866  -0.0579   1.0000   0.0500
 -18.250  -1.1022   0.07032   0.06477  -0.0588   1.0000   0.0507
 -18.000  -1.1093   0.06665   0.06105  -0.0595   1.0000   0.0517
 -17.750  -1.1138   0.06337   0.05769  -0.0601   1.0000   0.0525
 -17.500  -1.1169   0.06032   0.05458  -0.0605   1.0000   0.0535
 -17.250  -1.1193   0.05739   0.05159  -0.0608   1.0000   0.0547
 -17.000  -1.1199   0.05474   0.04886  -0.0610   1.0000   0.0556
 -16.750  -1.1226   0.05193   0.04600  -0.0610   1.0000   0.0569
 -16.500  -1.1261   0.04914   0.04316  -0.0609   1.0000   0.0584
 -16.250  -1.1271   0.04667   0.04064  -0.0606   1.0000   0.0598
 -16.000  -1.1262   0.04445   0.03837  -0.0602   1.0000   0.0614
 -15.750  -1.1259   0.04225   0.03613  -0.0597   1.0000   0.0633
 -15.500  -1.1260   0.04011   0.03397  -0.0589   1.0000   0.0658
 -15.250  -1.1245   0.03818   0.03201  -0.0581   1.0000   0.0688
 -15.000  -1.1235   0.03631   0.03015  -0.0570   1.0000   0.0728
 -14.750  -1.1213   0.03463   0.02846  -0.0558   1.0000   0.0778
 -14.500  -1.1176   0.03314   0.02697  -0.0545   1.0000   0.0832
 -14.250  -1.1127   0.03183   0.02565  -0.0531   1.0000   0.0873
 -14.000  -1.1082   0.03058   0.02437  -0.0515   1.0000   0.0912
 -13.750  -1.1014   0.02955   0.02329  -0.0498   1.0000   0.0942
 -13.500  -1.0961   0.02852   0.02223  -0.0479   1.0000   0.0964
 -13.250  -1.0938   0.02741   0.02111  -0.0456   1.0000   0.0989
 -13.000  -1.0906   0.02646   0.02013  -0.0431   1.0000   0.1015
 -12.750  -1.0866   0.02564   0.01928  -0.0405   1.0000   0.1038
 -12.500  -1.0718   0.02489   0.01847  -0.0398   0.9994   0.1059
 -12.250  -1.0512   0.02381   0.01739  -0.0406   0.9975   0.1090
 -12.000  -1.0296   0.02285   0.01642  -0.0413   0.9949   0.1122
 -11.750  -1.0069   0.02202   0.01556  -0.0420   0.9914   0.1152
 -11.500  -0.9840   0.02126   0.01477  -0.0425   0.9878   0.1180
 -11.250  -0.9614   0.02036   0.01388  -0.0433   0.9838   0.1223
 -11.000  -0.9357   0.01958   0.01310  -0.0444   0.9806   0.1272
 -10.750  -0.9128   0.01883   0.01236  -0.0449   0.9769   0.1327
 -10.500  -0.8916   0.01809   0.01165  -0.0449   0.9712   0.1404
 -10.250  -0.8674   0.01731   0.01095  -0.0456   0.9671   0.1542
 -10.000  -0.8409   0.01669   0.01039  -0.0465   0.9632   0.1689
  -9.750  -0.8180   0.01619   0.00992  -0.0464   0.9568   0.1778
  -9.500  -0.7875   0.01577   0.00948  -0.0477   0.9531   0.1846
  -9.250  -0.7545   0.01531   0.00904  -0.0496   0.9502   0.1914
  -9.000  -0.7244   0.01498   0.00869  -0.0507   0.9448   0.1974
  -8.750  -0.6928   0.01458   0.00827  -0.0522   0.9387   0.2021
  -8.500  -0.6577   0.01416   0.00786  -0.0544   0.9338   0.2072
  -8.250  -0.6291   0.01385   0.00753  -0.0551   0.9250   0.2119
  -8.000  -0.5947   0.01356   0.00720  -0.0569   0.9172   0.2161
  -7.750  -0.5696   0.01319   0.00683  -0.0570   0.9060   0.2218
  -7.500  -0.5402   0.01288   0.00649  -0.0578   0.8948   0.2264
  -7.250  -0.5131   0.01264   0.00620  -0.0580   0.8818   0.2304
  -7.000  -0.4881   0.01245   0.00594  -0.0577   0.8684   0.2333
  -6.750  -0.4670   0.01220   0.00565  -0.0568   0.8553   0.2379
  -6.500  -0.4473   0.01197   0.00539  -0.0554   0.8435   0.2438
  -6.250  -0.4278   0.01179   0.00518  -0.0540   0.8324   0.2486
  -5.750  -0.3919   0.01142   0.00476  -0.0504   0.8113   0.2608
  -5.500  -0.3733   0.01126   0.00457  -0.0487   0.8014   0.2683
  -5.250  -0.3578   0.01104   0.00438  -0.0464   0.7909   0.2781
  -5.000  -0.3411   0.01086   0.00419  -0.0443   0.7811   0.2896
  -4.500  -0.3116   0.01045   0.00385  -0.0393   0.7570   0.3220
  -4.250  -0.2968   0.01029   0.00370  -0.0367   0.7431   0.3369
  -4.000  -0.2817   0.01015   0.00357  -0.0342   0.7266   0.3505
  -3.750  -0.2660   0.01004   0.00345  -0.0317   0.7110   0.3628
  -3.500  -0.2501   0.00997   0.00334  -0.0292   0.6945   0.3751
  -3.250  -0.2357   0.00992   0.00326  -0.0265   0.6770   0.3857
  -3.000  -0.2198   0.00992   0.00320  -0.0240   0.6608   0.3955
  -2.750  -0.2060   0.00990   0.00315  -0.0210   0.6461   0.4058
  -2.500  -0.1884   0.00989   0.00311  -0.0189   0.6334   0.4150
  -2.250  -0.1716   0.00985   0.00307  -0.0166   0.6224   0.4261
  -2.000  -0.1541   0.00982   0.00303  -0.0144   0.6103   0.4379
  -1.750  -0.1356   0.00979   0.00300  -0.0125   0.5986   0.4508
  -1.500  -0.1189   0.00977   0.00298  -0.0102   0.5869   0.4633
  -1.250  -0.0984   0.00973   0.00295  -0.0086   0.5776   0.4738
  -1.000  -0.0795   0.00971   0.00294  -0.0067   0.5684   0.4853
  -0.750  -0.0591   0.00969   0.00292  -0.0052   0.5582   0.4947
  -0.500  -0.0399   0.00970   0.00291  -0.0033   0.5468   0.5046
  -0.250  -0.0195   0.00969   0.00291  -0.0018   0.5352   0.5136
   0.000   0.0000   0.00970   0.00291   0.0000   0.5243   0.5242
   0.250   0.0195   0.00969   0.00291   0.0018   0.5136   0.5352
   0.500   0.0400   0.00970   0.00291   0.0033   0.5046   0.5467
   0.750   0.0592   0.00969   0.00292   0.0052   0.4949   0.5585
   1.000   0.0797   0.00971   0.00294   0.0067   0.4858   0.5684
   1.250   0.0989   0.00972   0.00295   0.0085   0.4747   0.5776
   1.500   0.1189   0.00977   0.00298   0.0102   0.4631   0.5868
   1.750   0.1357   0.00979   0.00300   0.0125   0.4505   0.5981
   2.000   0.1541   0.00982   0.00303   0.0145   0.4375   0.6102
   2.250   0.1716   0.00985   0.00307   0.0166   0.4263   0.6227
   2.500   0.1886   0.00988   0.00311   0.0188   0.4154   0.6339
   3.000   0.2199   0.00992   0.00320   0.0239   0.3957   0.6610
   3.250   0.2355   0.00992   0.00326   0.0265   0.3860   0.6784
   3.500   0.2502   0.00997   0.00334   0.0292   0.3751   0.6944
   3.750   0.2661   0.01004   0.00345   0.0317   0.3629   0.7112
   4.000   0.2816   0.01014   0.00357   0.0342   0.3508   0.7279
   4.250   0.2971   0.01029   0.00370   0.0367   0.3373   0.7427
   4.500   0.3116   0.01045   0.00385   0.0393   0.3220   0.7575
   5.000   0.3414   0.01085   0.00419   0.0443   0.2898   0.7809
   5.250   0.3577   0.01104   0.00438   0.0464   0.2777   0.7909
   5.500   0.3733   0.01126   0.00457   0.0487   0.2679   0.8014
   5.750   0.3920   0.01141   0.00476   0.0504   0.2609   0.8115
   6.250   0.4280   0.01179   0.00518   0.0539   0.2487   0.8325
   6.500   0.4473   0.01197   0.00539   0.0554   0.2434   0.8432
   6.750   0.4673   0.01219   0.00565   0.0567   0.2381   0.8557
   7.000   0.4884   0.01245   0.00594   0.0577   0.2332   0.8683
   7.250   0.5132   0.01264   0.00620   0.0580   0.2303   0.8816
   7.500   0.5404   0.01288   0.00649   0.0578   0.2262   0.8947
   7.750   0.5698   0.01319   0.00683   0.0570   0.2214   0.9062
   8.000   0.5952   0.01357   0.00720   0.0568   0.2159   0.9174
   8.250   0.6297   0.01385   0.00753   0.0550   0.2118   0.9253
   8.500   0.6580   0.01416   0.00785   0.0543   0.2072   0.9338
   8.750   0.6933   0.01457   0.00826   0.0521   0.2022   0.9387
   9.000   0.7246   0.01498   0.00868   0.0507   0.1977   0.9446
   9.250   0.7551   0.01529   0.00903   0.0495   0.1927   0.9502
   9.500   0.7880   0.01577   0.00948   0.0476   0.1844   0.9531
   9.750   0.8188   0.01619   0.00991   0.0463   0.1776   0.9570
  10.000   0.8411   0.01670   0.01039   0.0464   0.1679   0.9635
  10.250   0.8685   0.01728   0.01093   0.0454   0.1552   0.9671
  10.500   0.8926   0.01808   0.01164   0.0447   0.1404   0.9713
  10.750   0.9135   0.01881   0.01234   0.0448   0.1326   0.9769
  11.000   0.9367   0.01957   0.01308   0.0442   0.1271   0.9807
  11.250   0.9628   0.02033   0.01385   0.0431   0.1225   0.9840
  11.500   0.9854   0.02123   0.01474   0.0423   0.1181   0.9880
  11.750   1.0081   0.02200   0.01554   0.0418   0.1150   0.9915
  12.000   1.0309   0.02283   0.01640   0.0411   0.1121   0.9951
  12.250   1.0528   0.02378   0.01735   0.0403   0.1090   0.9977
  12.500   1.0733   0.02487   0.01845   0.0395   0.1060   0.9995
  12.750   1.0871   0.02560   0.01924   0.0405   0.1039   1.0000
  13.000   1.0911   0.02641   0.02009   0.0431   0.1015   1.0000
  13.250   1.0944   0.02737   0.02106   0.0455   0.0988   1.0000
  13.500   1.0970   0.02846   0.02217   0.0478   0.0964   1.0000
  13.750   1.1025   0.02948   0.02322   0.0497   0.0940   1.0000
  14.000   1.1091   0.03052   0.02431   0.0514   0.0908   1.0000
  14.250   1.1134   0.03180   0.02560   0.0530   0.0870   1.0000
  14.500   1.1188   0.03308   0.02691   0.0544   0.0832   1.0000
  14.750   1.1225   0.03457   0.02839   0.0557   0.0774   1.0000
  15.000   1.1246   0.03626   0.03009   0.0569   0.0723   1.0000
  15.250   1.1257   0.03813   0.03196   0.0579   0.0683   1.0000
  15.500   1.1276   0.04004   0.03389   0.0588   0.0656   1.0000
  15.750   1.1271   0.04222   0.03610   0.0595   0.0630   1.0000
  16.000   1.1280   0.04438   0.03829   0.0600   0.0612   1.0000
  16.250   1.1291   0.04658   0.04055   0.0604   0.0598   1.0000
  16.500   1.1281   0.04906   0.04307   0.0607   0.0582   1.0000
  16.750   1.1250   0.05182   0.04588   0.0608   0.0568   1.0000
  17.000   1.1224   0.05462   0.04874   0.0607   0.0555   1.0000
  17.250   1.1218   0.05730   0.05149   0.0605   0.0546   1.0000
  17.500   1.1192   0.06025   0.05450   0.0602   0.0534   1.0000
  17.750   1.1161   0.06330   0.05763   0.0598   0.0524   1.0000
  18.000   1.1116   0.06660   0.06098   0.0592   0.0515   1.0000
  18.250   1.1049   0.07024   0.06468   0.0585   0.0506   1.0000
  18.500   1.0966   0.07414   0.06864   0.0575   0.0498   1.0000
  18.750   1.0945   0.07733   0.07192   0.0567   0.0493   1.0000
  19.000   1.0909   0.08076   0.07544   0.0558   0.0486   1.0000
  19.250   1.0875   0.08421   0.07896   0.0548   0.0479   1.0000
<< Back to GOE 460 AIRFOIL (goe460-il)

Polar data table (+)

Polar graphs


<< Back to GOE 460 AIRFOIL (goe460-il)